Flight test results of the strapdown hexad inertial reference unit (SIRU). Volume 2: Test report

Results of flight tests of the Strapdown Inertial Reference Unit (SIRU) navigation system are presented. The fault tolerant SIRU navigation system features a redundant inertial sensor unit and dual computers. System software provides for detection and isolation of inertial sensor failures and continued operation in the event of failures. Flight test results include assessments of the system's navigational performance and fault tolerance. Performance shortcomings are analyzed

Initial specifications for van and aircraft

Proposed testing program for strapdown inertial system containing platform gyros and pendulous gyro

Use of motion sensors for autonomous monitoring of hydraulic environments

Low cost, miniaturized, commercial-off-the-shelf (COTS) motion sensors, collectively with processors, an energy source and other electronic circuitry can be packaged into very small volumes for autonomous operation. If such a system operates over short periods of time, or data acquisitions occur at a very low frequency, processor resources should be sufficient to manage offsets and errors. The paper analyzes a typical set of COTS accelerometers and gyroscopes, to indicate how best these can be used in hydraulic environments. Application examples such as river bed sediment monitoring, milk vat monitoring etc. are briefly discussed, with application oriented design approaches. Minimizing the power consumption to introduce a novel, rechargeable power supply design is briefly outlined

Digital flight control research

The results of studies which were undertaken to contribute to the design of digital flight control systems, particularly for transport aircraft are presented. In addition to the overall design considerations for a digital flight control system, the following topics are discussed in detail: (1) aircraft attitude reference system design, (2) the digital computer configuration, (3) the design of a typical digital autopilot for transport aircraft, and (4) a hybrid flight simulator

Space shuttle navigation analysis. Volume 2: Baseline system navigation

Studies related to the baseline navigation system for the orbiter are presented. The baseline navigation system studies include a covariance analysis of the Inertial Measurement Unit calibration and alignment procedures, postflight IMU error recovery for the approach and landing phases, on-orbit calibration of IMU instrument biases, and a covariance analysis of entry and prelaunch navigation system performance

Design of strapdown gyroscopes for a dynamic environment Interim scientific report

Error analysis for single degree of freedom integrating gyro, and figure of merit relating gyro errors to orientation error of strapdown inertial reference syste

Inertial Navigation for Quadrotor Using Kalman Filter with Drift Compensation

The main disadvantage of an Inertial Navigation System is a low accuracy due to noise, bias, and drift error in the inertial sensor. This research aims to develop the accelerometer and gyroscope sensor for quadrotor navigation system, bias compensation, and Zero Velocity Compensation (ZVC). Kalman Filter is designed to reduce the noise on the sensor while bias compensation and ZVC are designed to eliminate the bias and drift error in the sensor data. Test results showed the Kalman Filter design is acceptable to reduce the noise in the sensor data. Moreover, the bias compensation and ZVC can reduce the drift error due to integration process as well as improve the position estimation accuracy of the quadrotor. At the time of testing, the system provided the accuracy above 90 % when it tested indoor